US7740201B2 - Device and method for floor heating in an aircraft - Google Patents
Device and method for floor heating in an aircraft Download PDFInfo
- Publication number
- US7740201B2 US7740201B2 US10/582,700 US58270004A US7740201B2 US 7740201 B2 US7740201 B2 US 7740201B2 US 58270004 A US58270004 A US 58270004A US 7740201 B2 US7740201 B2 US 7740201B2
- Authority
- US
- United States
- Prior art keywords
- hollow chambers
- floor
- aircraft
- accordance
- panels
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 238000010438 heat treatment Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims description 22
- 239000002699 waste material Substances 0.000 claims abstract description 53
- 238000001816 cooling Methods 0.000 claims abstract description 10
- 238000005485 electric heating Methods 0.000 claims description 15
- 239000000203 mixture Substances 0.000 claims description 9
- 238000001125 extrusion Methods 0.000 claims description 6
- 238000009413 insulation Methods 0.000 claims description 6
- 238000002156 mixing Methods 0.000 claims description 6
- 239000012530 fluid Substances 0.000 claims 5
- 238000004891 communication Methods 0.000 claims 4
- 230000005611 electricity Effects 0.000 claims 1
- 238000002955 isolation Methods 0.000 claims 1
- 238000013022 venting Methods 0.000 claims 1
- 239000012774 insulation material Substances 0.000 description 11
- 239000000463 material Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 206010034568 Peripheral coldness Diseases 0.000 description 1
- 229920005830 Polyurethane Foam Polymers 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011496 polyurethane foam Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0614—Environmental Control Systems with subsystems for cooling avionics
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Definitions
- This invention relates to a device and a method for floor heating in an aircraft.
- the aim of the invention is to provide an improved solution for the heating of the floor of an aircraft, which solution, if possible, should be achieved without having to generate additional current.
- the method according to the invention makes use of the fact that, nowadays, an extensive range of electronic equipment is provided in an aircraft which is cooled with air so as to guarantee correct function.
- This warm waste air which originates from the cooling of electronic equipment in the aircraft is available at next to no cost, and in accordance with the method proposed by the invention, it is conveyed through hollow chambers in panels which make up the aircraft floor.
- the aircraft floor is used as a heat exchanger between the hot electronics waste air and the cold aircraft structure, whereby a temperature is achieved on the floor surface which is pleasant for passengers and which prevents the formation of ice on the floor in freight aircraft.
- the warm waste air is conveyed through the floor panels along the length of the aircraft, and particularly preferably in opposition to the flight direction.
- This makes it possible and easy to convey the warm waste air, after flowing through the hollow chambers in the panels which make up the floor, through the floor panels of the aircraft cargo hold door so that this can be heated up as well.
- the warm waste air flows out into the aircraft fuselage after having flowed through the floor panels of the cargo hold door.
- other means of disposing of the warm waste air used to heat the floor and the cargo hold door can be provided.
- the warm waste air originates from what in the jargon of persons skilled in the art is often called the “avionics bay” of the aircraft, in which a large amount of the electronic equipment in an aircraft is kept.
- This type of avionics bay is usually located in the front section of an aircraft beneath the aircraft cockpit.
- any warm waste air which originates from the cooling of electronic components can be used in order to heat the floor and/or the cargo hold door.
- several supply lines are required to the floor and/or to the cargo hold door in order to convey the warm waste air from the different locations of electronic components to the floor and/or to the cargo hold door.
- the warm waste air which originates from the cooling of electronic equipment in the aircraft is not hot enough and/or is not available in sufficient quantities in order to heat the floor and/or the cargo hold door as required, it is proposed in accordance with a further development of the method according to the invention that the warm electronics waste air is mixed with hot engine bleed air.
- the hot engine bleed air is available in sufficient quantities.
- the hot engine bleed air is mixed in before the warm electronics waste air is supplied to the hollow chambers of the floor.
- waste air which originates from the cooling of electronic equipment in the aircraft is mixed with hot engine bleed air at two points, one before the waste air is used to heat the floor, and the other before the waste air is used to heat the cargo hold door, if so after it has flowed through the floor. In this way, individual quantities of heat can be supplied to the floor and the cargo hold door.
- the panels which make up the floor and/or the corresponding elements of the cargo hold door are provided with additional electric heating.
- the additional electric heating only produces the additional quantity of heat which is necessary for the required heating of the floor and/or the cargo hold door so that also this version of the method according to the invention is more economic with regard to energy than established, purely electrically-based solutions.
- a forced flow is generated in the panels of the floor or the cargo hold door, for example by means of ventilators or similar, in order to improve and even out the heat transfer.
- the floor heating for an aircraft includes continuous first hollow chambers which are formed within panels which make up the aircraft floor. Associated with the first hollow chambers is a feed line for warm waste air which originates from the cooling of electronic equipment in the aircraft. In this way, the aforementioned warm air can be used specifically for heating the aircraft floor.
- the first hollow chambers in the panels extend along the length of the aircraft.
- the warm waste air can then flow through the floor counter to the flight direction, and can at the end of the cargo hold or the aircraft cabin be used for the heating of still other parts.
- the first hollow chambers are in flow connection with second hollow chambers which are provided in floor panels of the aircraft cargo hold door. After flowing through the first hollow chambers, and at the same time heating up the floor, the warm waste air can then flow through the second hollow chambers of the cargo hold door in order to heat up the latter as well.
- the second hollow chambers can lead out freely into the aircraft fuselage, but separate outlet lines can also be provided for the waste air from the second hollow chambers.
- the feed line associated with the first hollow chambers serves to join the first hollow chambers with the previously mentioned avionics bay of the aircraft. If warm waste air from the cooling of electronic equipment is to be conveyed from another point or from several points in the aircraft to the first hollow chambers, the feed line must be in flow connection with this point or these points. Several separate feed lines can also be used which each convey warm electronics waste air from the location point of the electronic equipment to the first hollow chambers.
- an additional feed line which connects the first hollow chambers with hot engine bleed air. If the available electronics waste air is not sufficient, either with regard to quantity and/or temperature, additional warm air from another source, and which is available in sufficient quantities, can thereby be supplemented to the first hollow chambers. If so required, the hot engine bleed air can also heat the floor and/or the cargo hold door without any electronics waste air.
- the additional feed line is positioned in such a way that the hot engine bleed air can be mixed with the waste air originating from the cooling of electronic equipment in the aircraft before entering into the first hollow chambers. If required or desired, the feed lines can contain regulation valves which, in conjunction with the temperature sensors, set a pre-specified mix temperature with which the mix of electronics waste air and hot engine bleed air flows into the first hollow chambers.
- hot engine bleed air can be mixed at several points with the warm waste air originating from the cooling of electronic equipment in the aircraft, e.g., before the waste air enters into the first hollow chambers and moreover, once again before the waste air enters into the second hollow chambers.
- a simple possibility for quantity regulation of the mixed engine bleed air is to choose the corresponding flow cross-section of the supply line or feed line with which the hot engine bleed air is conveyed to the mixing point in such a way that the maximum quantity of heat which can flow through this line is the required quantity.
- the temperature for example of the floor and the cargo hold door, can be individually set.
- additional electric heating can be provided to the panels which make up the floor and/or the cargo hold door.
- This additional electric heating can be provided, for example, by means of conventional electric heating mats which are positioned on the upper side and/or the lower side of the panels which make up the floor. If the upper side of the floor needs to be heavy duty, the electric heating mats are preferably only placed on the lower side of the panels.
- additional electric heating can also be provided by means of electric heating coils or heating wires integrated into the hollow chambers of the floor and the cargo hold door.
- This embodiment can be used as an alternative to or in addition to the aforementioned additional heating by means of electric heating mats.
- the floor heating according to the invention is still more economical than conventional heating using only electric heating mats because, according to the invention, only that portion of heat needs to be generated electrically that may be required in addition to the heat which has already been provided in the electronics waste air.
- ventilators are positioned in the hollow chambers of the floor and/or the cargo hold, and these generate a forced flow of warm air through the hollow chambers.
- the panels which make up the floor are preferably thermally uncoupled from any structure which supports the floor so as to minimize heat loss from the panels to the structure.
- the panels are provided with thermal insulation on their lower side at points where they are not in contact with the structure which supports the floor.
- This thermal insulation can, for example, be in the form of panels or mats, and be made from a material which is generally familiar to experts in this field for this specific purpose.
- a layer of rigid insulation material is preferably chosen so that the load capacity of the floor is not negatively affected.
- the panels which make up the floor are preferably profile members produced by extrusion, in particular by continuous extrusion.
- the hollow chambers required for conveying the warm waste air are cost effectively produced as part of the extrusion process.
- FIG. 1 shows a schematic, partially cut away side view of a freight aircraft
- FIG. 2 shows a longitudinal section through a portion of a floor system which separates the cargo hold from the bilge of the aircraft
- FIG. 3 shows a cross-section through the floor system from FIG. 2 .
- FIG. 1 schematically illustrates the fuselage 10 of a freight aircraft.
- a cockpit section 12 below which there is an avionics bay 14 in which a large amount of the electronic equipment for the aircraft is kept.
- electronic equipment here means, for example, electronic equipment which is required for the navigation of the aircraft and also for the control of a number of components in the aircraft.
- the cargo hold 16 takes up the largest part of the fuselage 10 .
- the cargo hold 16 has a floor 20 made up from panels 18 which separates the cargo hold 16 from a bilge 22 located underneath the floor 20 .
- a cargo hold hatch or door 24 which is shown in FIG. 1 in closed position, and which in open position serves as a ramp by means of which the cargo hold 16 can be reached from outside.
- the panels 18 are extruded profile members in which the first hollow chambers 26 extend along the whole length of the floor 20 .
- these profile elements are made from an aluminium alloy.
- a feed line 28 extends between the front end of the panels 18 (as seen in the direction of flight) and the avionics bay 14 , by means of which the warm waste air used to cool the electronic equipment in the avionics bay 14 can be conveyed to the first hollow chambers 26 .
- a distributor not shown in the figures, ensures that there is even distribution of warm waste air to all of the first hollow chambers 26 of the panels 18 .
- connection line 30 the first hollow chambers 26 of the panels 18 are in flow connection with the second hollow chambers 32 which are provided in the floor panels 34 of the cargo hold door 24 .
- the floor panels 34 are extruded profile elements similar to the panels 18 of the floor 20 .
- the second hollow chambers 32 in the example illustrated end into the aircraft fuselage 10 .
- FIG. 1 shows feed lines 33 and 35 , respectively, for connecting the first and second hollow chambers 26 , 32 to the engine for receiving hot bleed air.
- the panels 18 of the floor 20 are fastened in a way not shown by their lower side onto supports 36 which are part of a structure which supports the floor 20 .
- the position of the supports 36 generally corresponds to the position of seat track adapters 38 which extend cross-wise to the boards 18 and by means of which seats can be fastened to the floor 20 .
- a layer 40 of rigid insulation material is positioned between the lower side of the boards 18 and the upper side of each support 26 exposed to the latter.
- rigid insulation material here means an insulation material which is not, or at least not noticeably compressed when subjected to pressure. It does not, therefore, affect the loading capacity of the floor 20 .
- a layer of insulation material 42 is applied to the lower side of the panels 18 which is considerably thicker than the layer 40 of rigid insulation material.
- the insulation material 42 does not need to be rigid because it does not have to withstand pressure.
- the insulation material 42 can, for example, be elements made from polyurethane foam or any other foam suitable for heat insulation which are stuck onto the panels 18 . It is also possible to incorporate the layer of insulation material 42 with the panels 18 during the extrusion process so that it forms one part with the panels 18 , for example by means of co-extrusion.
- the outer side of the insulation material 42 which is not in contact with the panels 18 can be covered with a layer 44 of highly reflective material.
- conventional electrical heating mat 43 can also be positioned above or below the panel hollow chambers 26 .
- electrical heating coils or wires 47 can be placed within the hollow chambers 26 to deliver more heat to the flow of waste air.
- the function of the heatable floor system is described.
- air is injected into the avionics bay 14 .
- the air takes heat from the electronic equipment and flows as warm waste air through the feed line 28 into the first hollow chambers 26 of the panels 18 of the floor 20 .
- the warm waste air flows lengthwise and against the direction of flight through the whole floor 20 (see the arrow v which symbolises the flow in FIG. 2 ).
- a member which is not illustrated collects the air emerging from the first hollow chambers 26 and passes it on to a connection line 30 from which the air flows into the second hollow chambers 32 , if so required by means of a second distributor, not illustrated here, which are incorporated into the floor panels 34 of the cargo hold door 24 .
- a second distributor not illustrated here, which are incorporated into the floor panels 34 of the cargo hold door 24 .
- the now cooled down air flows out into the aircraft fuselage 10 .
- this air can be conveyed to the outside in a controlled manner.
- both the floor 20 and the floor panels 34 of the cargo hold door 24 are heated to a pleasant temperature by the warm electronics waste air. If the electronics waste air available is insufficient with regard to temperature and quantity for the heating of the floor 20 and/or the floor panels 34 , hot engine bleed air can be admixed. If desired, as shown schematically in FIG. 3 , a ventilator 39 may be used to generate a forced flow through the first hollow chambers 26 .
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Central Heating Systems (AREA)
- Floor Finish (AREA)
- Air-Conditioning For Vehicles (AREA)
- Resistance Heating (AREA)
- Steam Or Hot-Water Central Heating Systems (AREA)
Abstract
Description
Claims (22)
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10361655A DE10361655B4 (en) | 2003-12-30 | 2003-12-30 | Device and method for underfloor heating in an aircraft |
DE10361655 | 2003-12-30 | ||
DE10361655.1 | 2003-12-30 | ||
PCT/EP2004/014857 WO2005063570A1 (en) | 2003-12-30 | 2004-12-30 | Device and method for floor heating in an aircraft |
Publications (2)
Publication Number | Publication Date |
---|---|
US20070125908A1 US20070125908A1 (en) | 2007-06-07 |
US7740201B2 true US7740201B2 (en) | 2010-06-22 |
Family
ID=34716245
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/582,700 Active 2025-08-22 US7740201B2 (en) | 2003-12-30 | 2004-12-30 | Device and method for floor heating in an aircraft |
Country Status (10)
Country | Link |
---|---|
US (1) | US7740201B2 (en) |
EP (1) | EP1699689B1 (en) |
JP (1) | JP4617469B2 (en) |
CN (1) | CN100448744C (en) |
AT (1) | ATE493336T1 (en) |
BR (1) | BRPI0418161A (en) |
CA (1) | CA2551933C (en) |
DE (2) | DE10361655B4 (en) |
RU (1) | RU2385827C2 (en) |
WO (1) | WO2005063570A1 (en) |
Cited By (6)
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US20090305622A1 (en) * | 2006-01-12 | 2009-12-10 | Airbus Deutschland Gmbh | Process and system for controlling the pressure in an aircraft cabin |
US20140291449A1 (en) * | 2011-11-23 | 2014-10-02 | Diehl Aerospace Gmbh | Device for heating a portion of a cabin floor in an aircraft cabin |
US9623973B2 (en) | 2009-07-06 | 2017-04-18 | Airbus Operations Gmbh | Cooling concept for fuel cell emergency power supply |
US9914522B2 (en) | 2014-10-29 | 2018-03-13 | Airbus Operations Gmbh | Floor panel for an aircraft, and an aircraft comprising such a floor panel |
US10207804B1 (en) * | 2015-03-18 | 2019-02-19 | Amazon Technologies, Inc. | Temperature-controlled payload container |
US10377498B2 (en) * | 2016-01-21 | 2019-08-13 | The Boeing Company | Aircraft and associated method for providing electrical energy to an anti-icing system |
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US8608110B2 (en) * | 2004-11-23 | 2013-12-17 | Biosphere Aerospace, Llc | Cargo aircraft system |
US8708282B2 (en) * | 2004-11-23 | 2014-04-29 | Biosphere Aerospace, Llc | Method and system for loading and unloading cargo assembly onto and from an aircraft |
DE102007049926A1 (en) * | 2007-10-18 | 2009-04-23 | Airbus Deutschland Gmbh | System and method for air conditioning at least a portion of an aircraft |
US20090114773A1 (en) * | 2007-11-05 | 2009-05-07 | Helou Jr Elie | Methods for fuel-efficient transportation of cargo by aircraft |
DE102009002404B4 (en) * | 2009-04-15 | 2015-11-19 | Airbus Operations Gmbh | Biegeträger for forming a bottom plate of a cargo compartment floor of an aircraft, base plate with such a bending beam and aircraft with such a bending beam |
EP2456661B1 (en) * | 2009-07-21 | 2015-01-21 | Telair International GmbH | Floor element for a loading deck of an aircraft |
JP2011183922A (en) * | 2010-03-08 | 2011-09-22 | Mitsubishi Heavy Ind Ltd | Anti-icing and deicing device at wing leading edge part in aircraft and main wing of aircraft |
JP5582927B2 (en) * | 2010-08-30 | 2014-09-03 | 三菱重工業株式会社 | Aircraft deicing system and aircraft equipped with the same |
JP5772176B2 (en) * | 2011-04-18 | 2015-09-02 | スズキ株式会社 | Fuel cell vehicle |
WO2014027320A1 (en) * | 2012-08-14 | 2014-02-20 | Intertechnique | Improved utilization for aircraft airstair space and fuel cell system integration |
EP2712806B1 (en) * | 2012-09-28 | 2016-05-11 | Airbus Operations GmbH | A partition for a vehicle |
FR3008678B1 (en) * | 2013-07-16 | 2015-09-04 | Dassault Aviat | AIRCRAFT COMPRISING ELECTRICAL POWER EQUIPMENT AND VENTILATION SYSTEM FOR ELECTRICAL POWER EQUIPMENT, INTERNAL ELEMENT AND METHOD THEREOF |
CN103466092A (en) * | 2013-10-11 | 2013-12-25 | 中国商用飞机有限责任公司 | Heating system and method for door area |
CN104260891B (en) * | 2014-09-23 | 2016-08-24 | 中国商用飞机有限责任公司 | Method and system for ventilating and heating aircraft cargo compartment |
US9567166B2 (en) * | 2014-10-10 | 2017-02-14 | Goodrich Corporation | Compact centrifugal air blowers for air cushion supported cargo loading platform |
US9555888B2 (en) | 2014-10-10 | 2017-01-31 | Goodrich Corporation | Pressure compensating air curtain for air cushion supported cargo loading platform |
US9643723B2 (en) | 2014-10-10 | 2017-05-09 | Goodrich Corporation | Slide bushing supported aircraft cargo loading systems and methods |
US10196146B2 (en) | 2014-10-10 | 2019-02-05 | Goodrich Corporation | Self propelled air cushion supported aircraft cargo loading systems and methods |
US9764840B2 (en) | 2014-10-10 | 2017-09-19 | Goodrich Corporation | Air cushion aircraft cargo loading systems and wireless charging unit |
US9511860B2 (en) | 2014-10-10 | 2016-12-06 | Goodrich Corporation | Air cushion aircraft cargo loading systems and wireless communication unit |
US9511861B2 (en) | 2014-10-10 | 2016-12-06 | Goodrich Corporation | Noise reduction barrier for air cushion supported aircraft cargo loading robot |
US10393225B2 (en) | 2015-01-05 | 2019-08-27 | Goodrich Corporation | Integrated multi-function propulsion belt for air cushion supported aircraft cargo loading robot |
JP6535167B2 (en) * | 2015-01-21 | 2019-06-26 | 三菱航空機株式会社 | Aircraft and fuselage cooling structure |
US9580250B2 (en) | 2015-01-30 | 2017-02-28 | Goodrich Corporation | Bushing cleaner systems and methods |
US10189572B2 (en) * | 2016-05-02 | 2019-01-29 | The Boeing Company | Systems and methods for preventing ice formation on portions of an aircraft |
DE102018132123A1 (en) * | 2018-09-14 | 2020-03-19 | Elbe Flugzeugwerke Gmbh | Floor system with heating unit |
DE102019133312A1 (en) * | 2019-12-06 | 2021-06-10 | Airbus Operations Gmbh | Heatable floor panel system for an aircraft, method for producing a heated floor panel, and aircraft |
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US3981466A (en) * | 1974-12-23 | 1976-09-21 | The Boeing Company | Integrated thermal anti-icing and environmental control system |
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US20020168184A1 (en) * | 1999-04-24 | 2002-11-14 | Juergen Meisiek | Electrically heated aircraft composite floor panel |
US6883590B1 (en) * | 1998-11-23 | 2005-04-26 | Plan Holding Gmbh | Self-supporting, modular prefabricated radiating panel |
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-
2003
- 2003-12-30 DE DE10361655A patent/DE10361655B4/en not_active Expired - Fee Related
-
2004
- 2004-12-30 CN CNB2004800374269A patent/CN100448744C/en not_active Expired - Fee Related
- 2004-12-30 JP JP2006546121A patent/JP4617469B2/en not_active Expired - Fee Related
- 2004-12-30 US US10/582,700 patent/US7740201B2/en active Active
- 2004-12-30 WO PCT/EP2004/014857 patent/WO2005063570A1/en active Application Filing
- 2004-12-30 AT AT04804442T patent/ATE493336T1/en not_active IP Right Cessation
- 2004-12-30 EP EP04804442A patent/EP1699689B1/en not_active Not-in-force
- 2004-12-30 RU RU2006121518/11A patent/RU2385827C2/en not_active IP Right Cessation
- 2004-12-30 DE DE602004030826T patent/DE602004030826D1/en active Active
- 2004-12-30 BR BRPI0418161-1A patent/BRPI0418161A/en not_active Application Discontinuation
- 2004-12-30 CA CA002551933A patent/CA2551933C/en not_active Expired - Fee Related
Patent Citations (15)
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Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
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US20090305622A1 (en) * | 2006-01-12 | 2009-12-10 | Airbus Deutschland Gmbh | Process and system for controlling the pressure in an aircraft cabin |
US8298055B2 (en) * | 2006-01-12 | 2012-10-30 | Airbus Operations Gmbh | Process and system for controlling the pressure in an aircraft cabin |
US9623973B2 (en) | 2009-07-06 | 2017-04-18 | Airbus Operations Gmbh | Cooling concept for fuel cell emergency power supply |
US20140291449A1 (en) * | 2011-11-23 | 2014-10-02 | Diehl Aerospace Gmbh | Device for heating a portion of a cabin floor in an aircraft cabin |
US9914522B2 (en) | 2014-10-29 | 2018-03-13 | Airbus Operations Gmbh | Floor panel for an aircraft, and an aircraft comprising such a floor panel |
US10207804B1 (en) * | 2015-03-18 | 2019-02-19 | Amazon Technologies, Inc. | Temperature-controlled payload container |
US10377498B2 (en) * | 2016-01-21 | 2019-08-13 | The Boeing Company | Aircraft and associated method for providing electrical energy to an anti-icing system |
Also Published As
Publication number | Publication date |
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EP1699689A1 (en) | 2006-09-13 |
DE10361655A1 (en) | 2005-08-04 |
DE10361655B4 (en) | 2007-10-04 |
US20070125908A1 (en) | 2007-06-07 |
CA2551933C (en) | 2009-04-07 |
DE602004030826D1 (en) | 2011-02-10 |
JP4617469B2 (en) | 2011-01-26 |
WO2005063570A1 (en) | 2005-07-14 |
ATE493336T1 (en) | 2011-01-15 |
RU2006121518A (en) | 2008-02-10 |
BRPI0418161A (en) | 2007-04-17 |
RU2385827C2 (en) | 2010-04-10 |
JP2007519554A (en) | 2007-07-19 |
CA2551933A1 (en) | 2005-07-14 |
EP1699689B1 (en) | 2010-12-29 |
CN100448744C (en) | 2009-01-07 |
CN1894131A (en) | 2007-01-10 |
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